Journal of computational fluids engineering (한국전산유체공학회지)

Korean Society of Computational Fluids Engineering (한국전산유체공학회)
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PREDICTION OF SEPARATION TRAJECTORY FOR TSTO LAUNCH VEHICLE USING DATABASE BASED ON STEADY STATE ANALYSIS

정상 해석 기반의 데이터베이스를 이용한 TST 비행체의 분리 궤도 예측

  • Jo, J.H. (Dept. of Aerospace Engineering, KAIST) ;
  • Ahn, S.J. (Dept. of Aerospace Engineering, KAIST) ;
  • Kwon, O.J. (Dept. of Aerospace Engineering, KAIST)
  • 조재현 (한국과학기술원 항공우주공학과) ;
  • 안상준 (한국과학기술원 항공우주공학과) ;
  • 권오준 (한국과학기술원 항공우주공학과)
  • Received : 2014.06.04
  • Accepted : 2014.06.20
  • Published : 2014.06.30
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Abstract

In this paper, prediction of separation trajectory for Two-stage-To-Orbit space launch vehicle has been numerically simulated by using an aerodynamic database based on steady state analysis. Aerodynamic database were obtained for matrix of longitudinal and vertical positions. The steady flow simulations around the launch vehicle have been made by using a 3-D RANS flow solver based on unstructured meshes. For this purpose, a vertex-centered finite-volume method was adopted to discretize inviscid and viscous fluxes. Roe's finite difference splitting was utilized to discretize the inviscid fluxes, and the viscous fluxes were computed based on central differencing. To validate this flow solver, calculations were made for the wind-tunnel experiment model of the LGBB TSTO vehicle configuration on steady state conditions. Aerodynamic database was constructed by using flow simulations based on test matrix from the wind-tunnel experiment. ANN(Artificial Neural Network) was applied to construct interpolation function among aerodynamic variables. Separation trajectory for TSTO launch vehicle was predicted from 6-DOF equation of motion based on the interpolated function. The result of present separation trajectory calculation was compared with the trajectory using experimental database. The predicted results for the separation trajectory shows fair agreement with reference[4] solution.

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References

  1. Decker. J.P., and Wihite. A.W., "Technology and methodology of separating two similer size aerospace vehicles within the atmosphere," AIAA Paper 1975-29.
  2. Murphy. K.J., Buning P.G., Pamadi B.N., Scallion. W.I., and Jones. K.M., "Overview of transonic to hypersonic stage separation tool development for multi-stage-to-orbit concepts," AIAA Paper 2004-2595.
  3. Pamadi B.N., Tartabini. P.V., and Starr. B.R., "Ascent, stage separation and glideback performance of a partially reusable small launch vehicle," AIAA Paper 2004-0876.
  4. 2007, Pamadi. B.N., Neirynck. T.A., Hotchko. N.J., Scallion. W.I., Murphy. K.J., Covell. P.F., "Simulation and Analyses of Stage Separation of Two-Stage Reusable Launch Vehicles," AIAA J, Vol.44,
  5. 1981, Roe, P.L., "Approximate Riemann Solvers, Parameter Vectors and Difference Scheme," Journal of Computational Physics, Vol.43, pp.357-372. https://doi.org/10.1016/0021-9991(81)90128-5
  6. 1992, Spalart, P.R., and Allmaras, S.R., "A One-Equation Turbulence Model for Aerodynamic flows," AIAA Paper 92-0439.
  7. 1993, Venkatakrishnan, V., "On the Accuracy of Limiters and Convergence to Steady State Solutions," AIAA Paper 93-0880.
  8. 1943, McCulloch, W.S. and Pitts, W., "A Logical Calculus of Ideas Immanent in Nervous Activity," Bulletin of Mathematical Biophysics, Vol.5, pp.115-133. https://doi.org/10.1007/BF02478259
  9. 1988, Broomhead, D.S. and Lowe, D., "Radial Basis Functions, Multi-variable Functional Interpolation and Adaptive Networks," Technical Report RSME Memorandum No. 4148, Royal Signals and Radar Establishment.
  10. Murphy K.J., Goodiff. S.L. and Erickson. G.E., "Experiment stage separation development in Langley's Unitary Plan Wind Tunnel," AIAA Paper 2004-4727.
  11. 2004, Pamadi, B.N., Tartabini, P.V. and Starr, B.R., "Ascent, Stage Separation and Glideback Performance of a Partially Reusable Small Launch Vehicle," AIAA Paper 2004-0876.
  12. 2003, Bordelon, W.J., Frost, A.L. and Reed, D.K., "Stage Separation Wind Tunnel tests of a Generic Two-Stage-to-Orbit Launch Vehicle," AIAA Paper 2003-4227.
  13. 2004, Murphy, K.J., Buning, P.G., Pamadi, B.N., Scallion, W.I., and Jones, K.M., "Overview of Transonic to Hypersonic Stage Separation Tool Development for Multi-Stage-to-Orbit concepts," AIAA2004-2595.
  14. 2004, Buning, P.G. and Gomez, R.J., "CFD Approaches for simulation of Wing-Body Stage Separation," AIAA Paper 2004-4838.
  15. 2004, Pamadi, B.N., Neirynck, T.A., Covell, P.F., Hotchko, N. and Bose, D., "Simulation and analyses of Staging Maneuvers of Next Generation Reusable Launch Vehicles," AIAA Paper 2004-5185.